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3 1176 01364 9885
NACA ARR No. L5F28
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
ADVANCE RESTRICTED REPORT
WIND-TUNNEL TESTS OF SPOILERS ON TAIL SURFACES
By Robert B. Liddell
StMMARY
Wind-tunnel tests have been made in two-dimensional
and three-dimensional flow to investigate the aero-
dynamic characteristics of spoilers on tail surfaces
for low-speed flight.
The test results indioated that spoilers on tail
surfaces showed little possibility of replacing conven-
tional control surfaces. Spoilers might be used as
auxiliary aids to conventional control surfaces if a
number of the disadvantages that they present can be
remedied or tolerated. These disadvantages consisted
principally of high drag, erratic action, and an adverse
effect on normal control-surface hinge moments.
A spoiler on the forward portion of the tail surface,
used alone or in conjunction with the conventional control
surface, gave unsatisfactory results because of its erratic
effect throughout the angle-cf-attack range. Spoilers
generally should be located on the rear portion of the
tail surface, but an auxiliary forward spoiler might be
advantageous in depressing the tail in the landing
maneuver. A forward auxiliary spoiler should be located
on the opposite side of the tail surface from the rear
spoiler, since two spoilers on the same side of the tail
surface tend to cancel the effects obtained by the use
of either spoiler alone.
INTRODUCTION
A number of modern airplanes have encountered
difficulty in landing because of inadequate elevator
control. Very large control deflections are required
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Liddell, Robert B. Wind-tunnel tests of spoilers on tail surfaces, report, August 1945; (https://digital.library.unt.edu/ark:/67531/metadc61542/m1/2/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.